航天器力限振动试验条件设计研究

航天器在研制过程中要经过一系列地面力学验证试验, 但在传统加速度控制振动试验中, 受试航天器或其部组件和试验台的连接机械阻抗与真实飞行状态存在很大差异, 如果仅采用加速度条件进行控制可能产生严重的"过试验" 现象. 美国早在20 世纪60 年代就已认识到这一问题, 但直到最近十几年才通过力限振动试验的办法加以解决. 力限振动试验技术分为力限振动试验条件设计技术和力限振动试验控制技术, 其中试验条件设计是开展振动试验的基础和依据. 本文对国内外力限振动试验技术的发展历程和重要成果进行了简述, 并结合我国力限振动试验技术的现状, 对力限振动试验技术在我国的应用和发展, 以及有待进一步研究的问题进行了展望. 

RESEARCH ON THE ESTIMATION OF FORCE SPECIFICATIONS FOR FORCE-LIMITED VIBRATION TESTING

In traditional vibration tests, the payload is mounted to a rigid fixture and the interface acceleration is controlled to a specified level based on a conservative estimate of the expected flight environment. The force- limited vibration testing is developed to alleviate the over-testing associated with impedance differences between the flexible flight mounting and the rigid test fixture. Force-limited vibration testing technology is composed of the calculation method of force specifications and the force-limited control technology in vibration testing, and the calculation of the force specifications is the most critical step of the force-limited vibration testing. This paper presents force-limited vibration testing technology and the calculation method of force specifications, and surveys comprehensively the development of the technology. And finally, according to the requirement of domestic space engineering, several research directions in force-limited vibration testing technology are stressed.